US20160040553A1 - Impingement ring element attachment and sealing - Google Patents

Impingement ring element attachment and sealing Download PDF

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Publication number
US20160040553A1
US20160040553A1 US14/781,819 US201414781819A US2016040553A1 US 20160040553 A1 US20160040553 A1 US 20160040553A1 US 201414781819 A US201414781819 A US 201414781819A US 2016040553 A1 US2016040553 A1 US 2016040553A1
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United States
Prior art keywords
ring element
impingement
impingement ring
groove
circumferential direction
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Abandoned
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US14/781,819
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English (en)
Inventor
Paul Headland
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Siemens AG
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Siemens AG
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Assigned to SIEMENS INDUSTRIAL TURBOMACHINERY LIMITED reassignment SIEMENS INDUSTRIAL TURBOMACHINERY LIMITED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HEADLAND, PAUL
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SIEMENS INDUSTRIAL TURBOMACHINERY LIMITED
Publication of US20160040553A1 publication Critical patent/US20160040553A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a turbine comprising at least two impingement ring elements which are coupled by a coupling ring element and to a method for manufacturing the turbine.
  • turbine parts such as inner walls or platforms
  • cooling systems are used for cooling the turbine parts.
  • cooling air systems are installed for providing a cooling air stream to the hot turbine parts and/or preventing the hot stream of combustion gases to escape past the inner and outer walls of the main flow annulus.
  • the space for installing a cooling air system and for providing an effective cooling circulation of the cooling fluid is limited.
  • complex cooling systems are expensive and the reliability is low.
  • a high amount of cooling air my affect negatively the turbine performance.
  • the cooling channels which supply the cooling fluid are covered by an annular impingement ring.
  • the annular impingement ring comprises a plurality of cooling holes through which the cooling fluid is exhausted from the cooling channel to a desired location within the gas turbine.
  • the impingement ring and the supporting structures to which the impingement ring is mounted comprise different thermal expansions with respect to the respective impingement ring such that air leakage due to gaps generated by the different thermal expansions is caused.
  • US 2005/0241314 A1 discloses a cooling structure for a gas turbine tailpipe.
  • An impingement cooling plate whose cross-section is approximately L-shaped comprises a multiple number of holes and is mounted by welding to a rib of a vane shroud of the gas turbine.
  • GB 2 035 466 A1 discloses a turbine shroud support with an impingement baffle.
  • An impingement baffle leg of the impingement baffle is mounted to a shroud of the gas turbine.
  • EP 1 500 789 A1 discloses an impingement cooled ring segment of a gas turbine, wherein an annular impingement ring element is mounted to a vane carrier.
  • EP 1 038 093 B1 discloses a turbine passive thermal valve for improved tip clearance control.
  • a cooling channel is formed between a shroud of a gas turbine and an impingement ring element, wherein through the impingement ring element either the cooling fluid flows to the inner shroud or away from the inner shroud.
  • U.S. Pat. No. 4,805,398 discloses a turbo-machine comprising annular impingement ring elements.
  • the annular impingement ring elements overlap each other along a circumferential direction in order to provide a closed ring-shaped impingement ring element arrangement.
  • EP 2 299 063 A1 discloses an impingement baffle for a gas turbine engine.
  • the impingement baffle is a one piece split impingement ring element with fastening elements at both free ends of the impingement ring element to enable the closing of the impingement ring element.
  • U.S. Pat. No. 4,337,016 A discloses apparatus for confining cooling air to a flowpath between an outer case and adjacent structure.
  • the sealing means is annular and has dual walls, a segmented ring and a segmented inner wall that is located radially inwardly of the segmented ring.
  • a turbine in particular a gas turbine, is presented.
  • the turbine comprises a support structure which extends along a circumferential direction of the turbine.
  • the supporting structure comprises a groove to which cooling air is guidable.
  • the groove extends along the circumferential direction.
  • the turbine furthermore comprises a first impingement ring element comprising a plurality of first holes and a second impingement ring element comprising a plurality of second cooling holes.
  • the first impingement ring element and the second impingement ring element are mounted one after another along the circumferential direction to the groove such that the groove is covered by the first impingement ring element and the second impingement ring element.
  • the turbine further comprises a first coupling ring element which is arranged between the first impingement ring element and the second impingement ring element such that the groove is covered by the first coupling ring element between the first impingement ring element and the second impingement ring element.
  • the first coupling ring element forms a sliding contact with the second impingement ring element such that a relative movement between the first coupling ring element and the second impingement ring element is providable.
  • a method for manufacturing a turbine in particular a gas turbine, is presented.
  • a supporting structure is formed which extends along a circumferential direction of the turbine.
  • the supporting structure comprises a groove through which cooling air is guidable.
  • the groove extends along the circumferential direction.
  • a first impingement ring element comprising a plurality of cooling holes and a second impingement ring element comprising a plurality of second cooling holes are formed.
  • the first impingement ring element and the second impingement ring element are mounted one after another along the circumferential direction to the groove such that the groove is covered by the first impingement ring element and the second impingement ring element.
  • a first coupling ring elements formed which extends between the first impingement ring element and the second impingement ring element along the circumferential direction such that the groove is covered by the first coupling ring between the first impingement ring element and the second impingement ring element.
  • the sliding contact between the first coupling ring and the second impingement ring element is formed such that a relative movement between the first coupling ring element and the second impingement ring element is providable.
  • the turbine may be in particular a gas turbine, for example for power generation or for aircraft propulsion.
  • the turbine comprises generally a rotary shaft which is rotatable around a rotary axis.
  • the rotary axis defines an axial direction of the gas turbine.
  • a direction crossing the rotary axis and being perpendicular to the rotary axis is denoted as the radial direction.
  • a direction running around the rotary axis with a constant radius to the rotary axis may be denoted as the circumferential direction.
  • a tangent of the circumferential direction is perpendicular to the radial direction and the axial direction.
  • the supporting structure denotes a structure of the gas turbine which is for example adapted for carrying blades, vanes or other housing parts of the turbine.
  • the supporting structure may comprise an inner vane carrier, an outer vane carrier, an inner shroud, an outer shroud, an inner housing and/or an outer housing.
  • the groove may be formed in a radial inner or outer surface of the supporting structure. Specifically, the groove may run along the circumferential direction and comprises a ring-shaped annular shape.
  • the groove is coupled to a cooling fluid inlet for injecting cooling fluid into the groove and may be coupled to a cooling fluid outlet from which the cooling fluid may be bled off from the groove.
  • the first and second impingement ring elements may be formed from metal or a composite fibre, wherein the first and second impingement ring elements are thin and have a plate and sheet metal-like structure.
  • the first and second impingement ring elements comprise respective first and second cooling holes through which the cooling fluid may flow between the groove and the location surrounding the respective impingement ring elements.
  • the first and second impingement ring elements may have an I-shaped, L-shaped or U-shaped profile.
  • first impingement ring element and the second impingement ring element are structurally different elements.
  • first impingement ring element and the second impingement ring element cannot be seen as integral and monolithically unique structure bur have to be understood as separate spatially spaced and along the circumferential direction adjacent non-overlapping impingement ring elements.
  • the first impingement ring element and the second impingement ring element are mounted one after another along the circumferential direction to the groove.
  • the first and second impingement ring elements may cover the groove along the circumferential direction and form together an annular ring-shaped profile.
  • the first impingement ring element and the second impingement ring element may only cover a certain section of the groove along the circumferential direction and may thus form an half ring-shaped profile.
  • the first coupling ring element may be of the same material as the first impingement ring element and the second impingement ring element.
  • the first coupling ring element may be made of metal material or fibre composite material.
  • the first coupling ring element is in slidable contact with at least one of the first impingement ring element and the second impingement ring element.
  • the first coupling ring element is fixed to the first impingement ring element and extends from the first impingement ring element along the circumferential direction to the second impingement ring element.
  • the first coupling ring element overlaps with the second impingement ring element and may slide along the second impingement ring element in the circumferential direction.
  • the first coupling ring element forms a floating and sliding contact with respect to the second impingement ring element.
  • the first coupling ring element comprises a radially inner and a radially outer surface.
  • the second impingement ring element comprises a radially inner surface and a radially outer surface.
  • the first coupling ring element contacts with its radially inner surface the radially outer surface of the second impingement ring element or contact with its radially outer surface the radially inner surface of the second impingement ring element.
  • the first coupling ring element bridges a gap (clearance) between the first impingement ring element and the second impingement ring element.
  • an impingement ring system which comprises at least two impingement ring elements, namely the first impingement ring element and the second impingement ring element.
  • the impingement ring element system is split into a number of ring elements, i.e. the at least first and second impingement ring elements, the thermal expansion of the impingement ring element is limited and reduced and allowing the first coupling ring element to slide over the adjacent surfaces of the respective first and second impingement ring elements.
  • a monolithically formed single strip-like impingement ring which extends all around the circumferential direction and forms an annular and ring-shaped profile.
  • the single strip-like conventional impingement ring has a large thermal expansion which is complicated to handle.
  • the impingement ring system is divided into a plurality of impingement ring elements such that at the interfaces between the respective impingement ring elements only smaller thermal expansions occur which are easier to handle in contrast to one huge thermal expansion generating one large gap.
  • the first coupling ring element is fixed to the first impingement ring element.
  • the first coupling ring element may also be fixed to the first impingement ring element, by any one of the group comprising forming integrally, welding, fusing, riveting and bonding for example.
  • the second impingement ring element comprises a guiding groove extending along the circumferential direction.
  • the guiding groove is formed for engaging the first coupling ring element such that the first coupling ring element is slidable within the guiding groove.
  • a U-shaped rail extending along the circumferential direction may be formed at the side faces of the second coupling ring. The U-shaped rails engages the first coupling ring element. Hence, the first coupling ring element is guided during a sliding motion between the second ring element and the first coupling ring element.
  • the guiding groove may be formed in such a way, that the first coupling ring element is slightly pressed against a respective surface of the second impingement ring element such that it is assured that the first coupling ring element keeps a respective sliding contact with the surface of the second impingement ring element, also during a sliding motion.
  • a gap between the second impingement ring element and the first coupling ring element is prevented which could cause undesired turbulences and uneven distribution of the cooling fluid within the groove around the respective impingement ring element.
  • the first coupling ring element comprises a first aperture (i.e. aperture region) such that the cooling air is flowable through the first aperture and at least some of the first cooling holes.
  • the first aperture may have a size which covers a plurality of respective first cooling holes or the aperture region may comprise a hole pattern which complies with a hole pattern of the first cooling holes such that the cooling holes of the first aperture are aligned with the first cooling holes such that cooling air may flow through the first cooling holes and the holes of the first aperture.
  • the first cooling ring element does not cover any or covers only some of the first cooling holes such that the cooling capacity is not negatively affected by attaching a first coupling ring element to the first impingement ring element.
  • the first coupling ring element comprises a second aperture such that the cooling air is flowable through the second aperture and some of the second cooling holes.
  • the second aperture may have a size which covers a plurality of respective first cooling holes or may comprise a hole pattern which complies with a hole pattern of the second cooling holes such that the cooling holes of the second aperture are aligned with the first cooling holes such that cooling air may flow through the second cooling holes and the holes of the second aperture.
  • the first cooling ring element does not cover any or covers only some of the second cooling holes such that the cooling capacity is not negatively affected by attaching a first coupling ring element to the second impingement ring element.
  • the first coupling ring element comprises an array of first apertures such that the cooling air is flowable through some of the first apertures and some of the first cooling holes and wherein the first coupling ring element comprises a second aperture such that the cooling air is flowable through the second aperture and some of the second cooling holes.
  • the first relative position can be at a relatively cold working condition of the turbine.
  • the first relative position can be when a gap between the first impingement ring element and the second impingement ring element is at or near a minimum.
  • the first coupling ring element comprises an array of first apertures such that cooling air is flowable through some of the first apertures and some of the first cooling holes, such that cooling air is flowable through some of the other first apertures only, and wherein the first coupling ring element comprises a second aperture such that cooling air is flowable through the second aperture and some of the second cooling holes.
  • the second relative position can be at a relatively hot working condition of the turbine.
  • the first relative position can be when a gap between the first impingement ring element and the second impingement ring element is at or near a maximum.
  • the first impingement ring element is elastically deformable.
  • the first impingement ring element and the groove are formed such that the first impingement ring element is inserted within the groove in a pre-stressed manner such that the first impingement ring element forms with the supporting structure a press fitting connection.
  • the first impingement ring element may be made of a metal material in order to provide the elastically deformable properties.
  • the first impingement ring element is in other words sprung into the groove in the supporting structure. This allows a simple assembly procedure and may provide a proper sealing on the contact surfaces between the first impingement ring element and the groove.
  • the second impingement ring element may also be formed elastically deformable and may also be inserted within the groove in a pre-stressed manner in order to form a press-fitting connection.
  • the first impingement ring element comprises a covering section which covers the groove and a retainer tab which protrudes from the covering section along an axial direction of the turbine.
  • the support structure comprises a retainer tab hole such that the retainer tab is arranged inside the retainer tab hole in a slidable manner at least along the circumferential direction.
  • the covering section denotes a section and a surface of the first impingement ring element which comprises a normal approximately in the radial direction.
  • the first impingement ring element may comprise a side section which has a normal approximately in the axial direction.
  • the covering section and the side section may form an L-shaped cross-section.
  • the first impingement ring element may comprise a further side section with a normal approximately in axial direction, such that the first impingement ring element has a U-shaped cross-section.
  • the retainer tab may protrude from the covering section or from the side section approximately along the axial direction.
  • the retainer tab recess is larger than the retainer recess such that if the retainer tab is inserted in the retainer tab recess, a loose-fit is generated such that the retainer tab floats inside the retainer tab recess specifically along the circumferential direction.
  • the first impingement ring element may comprise a plurality of retainer tabs and the groove may comprise respectively a plurality of retainer tab recesses. Furthermore, also the further used second and third impingement ring elements may comprise respective retainer tabs and the groove may comprise respective retainer tab recesses as described above for the first impingement ring element.
  • the slots i.e. the retainer tab recesses, are wider and larger than the respective retainer tabs on the respective impingement ring elements such that a thermal movement of the supporting structure and the respective impingement ring element is allowed.
  • the first impingement ring element comprises a first circumferential end face and (in circumferential direction opposed to the first circumferential end face) a further first circumferential end face.
  • the second impingement ring element comprises a second circumferential end face and (in circumferential direction opposed to the second circumferential end face) a further second circumferential end face.
  • the first circumferential end face and the second circumferential end face are arranged adjacent to each other along the circumferential direction such that the first coupling ring element extends between the first circumferential end face and the second circumferential end face along the circumferential direction.
  • the first circumferential end face and the second circumferential end face are arranged adjacent to each other and do not overlap each other.
  • the turbine further comprises a second coupling ring element.
  • the further first circumferential end face and the further second end face are arranged adjacent to each other along the circumferential direction such that the second coupling ring element extends between the further first circumferential end face and the further second circumferential end face along the circumferential direction.
  • the second coupling ring element forms a sliding contact with the second impingement ring element.
  • respective coupling ring elements may be attached for being coupled to an adjacent impingement ring element.
  • the respective coupling ring elements are fixed to one impingement ring element and are in slidable contact with an adjacent impingement ring element.
  • the turbine comprises a third impingement ring element comprising a plurality of third cooling holes.
  • the first impingement ring element, the second impingement ring element and the third impingement ring element are mounted one after another along the circumferential direction to the groove such that the groove is covered (completely or partially) by the first impingement ring element, the second impingement ring element and the third impingement ring element.
  • the turbine further comprises a third coupling ring element which extends between the first impingement ring element and the third impingement ring element along the circumferential direction such that the groove is covered by the third coupling ring element between the first impingement ring element and the third impingement ring element.
  • the third coupling ring element forms a sliding contact with the first impingement ring element and/or the third impingement ring element.
  • the turbine according to the present invention may comprise also three or a plurality of impingement ring elements which are coupled one after another along a circumferential direction and form an annular and ring-shaped impingement ring system.
  • the impingement ring elements may slide with respect to each other along the circumferential direction such that thermal expansions between the impingement ring elements along each other and with respect to the supporting structure may be balanced.
  • FIG. 1 shows a sectional view of a turbine according to an exemplary embodiment of the present invention
  • FIG. 2A illustrates schematically a first and second impingement ring element coupled by a first coupling ring element, wherein the turbine is in a hot working condition according to an exemplary embodiment of the present invention
  • FIG. 2B illustrates schematically a first and second impingement ring element coupled by a first coupling ring element, wherein the turbine is in a cold working condition according to an exemplary embodiment of the present invention
  • FIG. 3 shows a sectional view of a turbine according to an exemplary embodiment of the present invention, wherein a retainer tab of an impingement ring element is shown;
  • FIG. 4 shows an impingement ring element comprising two coupling ring elements according to an exemplary embodiment of the present invention.
  • FIG. 5 shows a schematical view of a turbine according to an exemplary embodiment of the present invention.
  • FIG. 1 shows a sectional view of a turbine 100 , in particular a gas turbine, wherein the turbine 100 comprises a supporting structure 101 , a first impingement ring element 110 , a second impingement ring element 120 and a first coupling ring element 130 .
  • the supporting structure 101 may be for example an inner shroud, an outer shroud, an inner housing or an outer housing of the turbine 100 , for example.
  • the supporting structure 101 is a vane carrier, for example.
  • the supporting structure 101 extends along a circumferential direction 102 .
  • the turbine comprises a rotary shaft which is rotatable around a rotary axis.
  • the rotary axis defines an axial direction 302 (see FIG. 3 ) of the gas turbine.
  • a direction crossing the rotary axis 301 and being perpendicular to the rotary axis is denoted as the radial direction 301 (see FIG. 3 ).
  • a direction running around the rotary axis with a constant radius to the rotary axis is denoted as the circumferential direction 102 .
  • a tangent of the circumferential direction 102 is perpendicular to the radial direction 301 and the axial direction 302 .
  • the supporting structure 101 comprises a groove 103 through which cooling air is guidable, wherein the groove 103 extends along the circumferential direction 102 .
  • the groove is covered by a first impingement ring element 110 comprising a plurality of first cooling holes and a second impingement ring element 120 comprising a plurality of second cooling holes.
  • the first impingement ring element 110 and the second impingement ring element 120 are mounted one after another along the circumferential direction 102 to the groove 103 .
  • a first coupling ring element 130 is arranged such that the groove 103 is covered by the first coupling ring element 130 between the first impingement ring element 110 and the second impingement ring element 120 .
  • the first coupling ring element 130 forms a sliding contact with the second impingement ring element 120 such that a relative movement between the first coupling ring element 130 and the second impingement ring element 120 is providable.
  • the first coupling ring element 130 is spatially fixed to the first impingement ring element 110 and is in floating/sliding contact with its free floating end located in an overlapping manner at the second impingement ring element 120 .
  • the first and second impingement ring elements 110 , 120 may move with respect to each other along the circumferential direction 103 such that the thermal expansion can be balanced.
  • At least two structurally separated impingement ring elements 110 , 120 are mounted within the groove 103 in order to cover the groove 103 .
  • An annular ring of the turbine 100 is split into at least two impingement ring elements 110 , 120 such that the overall thermal expansion between one impingement ring element 110 and an adjacent second impingement ring element 120 is reduced in comparison to a one piece annular ring.
  • the clearance is covered by the first coupling ring element 130 .
  • the different thermal expansions between the respective impingement ring elements 110 , 120 and the supporting structure 101 do not cause gaps or clearances through which cooling air may bleed off from the groove 103 in an uncontrolled manner.
  • respective sealing rings 104 may be attached to the supporting structure 101 in order to improve the cooling efficiency of the cooling fluid.
  • FIG. 2A and FIG. 2B show the respective impingement ring elements 110 , 120 and the first coupling ring element 130 . Furthermore, FIG. 2A and FIG. 2B show a bottom view of the respective impingement ring elements 110 , 120 and the first coupling ring element 130 .
  • the first coupling ring element 130 may be integrally formed with the first impingement ring element 110 and/or may be for example welded to the first impingement ring element 110 . Furthermore, the first coupling ring element 130 is in sliding contact with the second impingement ring element 120 . In order to assure that the first coupling ring element 130 is in slidable contact with the respective surface of the second impingement ring element 120 , the second impingement ring element 120 comprises a guiding groove 201 which engages the first coupling ring element 130 . Hence, the guiding groove 201 may form a guiding rail for the edges of the first coupling ring element 130 .
  • first coupling ring element 130 may comprise first apertures 202 .
  • the first apertures 202 may comprise a through-hole-like pattern and may be aligned with the first through-holes of the first impingement ring element 110 , such that the cooling fluid may flow through the first apertures 202 and the first through holes of the first impingement ring element 110 .
  • the first coupling ring element 130 comprises a second aperture 203 .
  • the second aperture 203 may have a larger area, wherein the area of the second aperture 203 is chosen for “covering” a plurality of second holes of the second impingement ring element 120 . It is meant that the second aperture 203 expand over an area such that a plurality of second holes of the second impingement ring element 120 remain unblocked. In the exemplary embodiment shown in FIG. 2A and FIG. 2B , the second aperture 203 expands over four second through-holes of the second impingement ring element 120 .
  • FIG. 2A shows an alignment of the first impingement ring element 110 and the second impingement ring element 120 , wherein the turbine 100 is in a hot working condition.
  • the supporting structure 101 which is generally made of a metal material, comprises a larger thermal expansion than the thin plate-like formed impingement ring elements 110 , 120 .
  • the supporting structure 101 increases its size more than the respective impingement ring elements 110 , 120 , a gap (clearance) between the circumferential end faces 111 , 121 of the respective impingement ring elements 110 , 120 axes.
  • the distance x of the respective circumferential end faces 111 , 121 is covered by the first coupling ring element 130 such that an uncontrolled bled off of cooling air is prevented.
  • the first coupling ring element 130 comprises respective through-holes also in the section where the first coupling ring element 130 overlaps the distance x.
  • FIG. 2B shows a cold working condition of the turbine 100 , where the distance x is reduced, such that the circumferential end faces 111 , 121 are located adjacent to each other and may abut each other along the circumferential direction 102 .
  • FIG. 3 shows a further exemplary embodiment of the present invention, wherein a mounting of the first impingement ring element 110 within the groove 103 is shown.
  • the first impingement ring element 110 is elastically deformable.
  • the first impingement ring element 110 and the groove 103 are formed with respect to each other such that the first impingement ring element 110 is inserted within the groove 103 in a pre-stressed manner such that the first impingement ring element 110 forms with the supporting structure 101 a press-fitting connection.
  • FIG. 3 For a better understanding, the radial direction 301 and the axial direction 302 of the turbine 100 is shown in FIG. 3 .
  • the first impingement ring element 110 may comprise a covering section 301 which may comprise a normal n in radial direction 301 .
  • the first impingement ring element 110 may further comprise two side sections 313 which extend from the covering section 311 generally along the radial direction 301 .
  • the side sections 313 may have a normal n which is parallel to a normal of respective groove sidewalls 304 .
  • the side sections 313 may be elastically bent together and after inserting the first impingement ring element 110 within the groove 103 , the side sections 313 are released such that the side sections 313 press against the groove sidewalls 304 such that a press fitting connection between the supporting structure 101 and the first impingement ring element 110 is formed.
  • the first impingement ring element 110 comprises a retainer tab 312 which protrudes along the axial direction 302 of the turbine 100 .
  • the support structure 101 comprises a retainer tab hole 303 , which is formed in the groove sidewall 304 , such that the retainer tab 312 is arranged inside the retainer tab hole 303 in a slidable manner at least along the circumferential direction 102 .
  • the retainer tab 312 may extend along the axial direction 302 from the covering section 311 or, as shown in FIG. 3 , from the side section 313 of the first impingement ring element 110 . If the retainer tab 312 is inserted in the retainer tab recess 303 , a movement of the first impingement ring element 110 along e.g. the radial direction 301 may be prevented such that the first impingement ring element 101 is prevented from leaving the groove 103 .
  • the retainer tab recess 303 is in circumferential direction 102 larger than the circumferential extension of the retainer tab 312 , the retainer tab 312 may move along the circumferential direction 102 and may thus balance the thermal expansions of the first impingement ring element 110 .
  • an air inlet 305 is shown, through which cooling air may be fed in or drained off from the groove 103 .
  • the cooling air is fed in or drained off along the axial direction 302 .
  • a further aperture 314 may be formed within the side section 313 .
  • FIG. 4 shows the first impingement ring element 110 .
  • the first impingement ring element 110 covers 1 ⁇ 3 of the circumference (i.e. the perimeter) of the groove 103 .
  • three impingement ring elements 110 , 120 are attached one after another along the circumferential 102 to the groove 103 .
  • the first impingement ring element 110 may comprise at each circumferential end faces 111 , 111 ′ respective first coupling ring elements 130 , 130 ′.
  • a plurality of respective retainer tabs 312 , 312 ′ are formed for being engaged by the respective retainer tab recesses 303 as shown in FIG. 3 .
  • FIG. 5 shows an exemplary view of a turbine section of the turbine 100 .
  • the turbine 100 comprises an outer housing 501 and an inner housing 502 , wherein the first impingement ring element 110 may be arranged there between.
  • the guide vane 503 with the respective inner and outer shrouds is shown, wherein an inner guide vane carrier 505 carries the guide vanes 503 .
  • the first impingement ring element 111 may be arranged between the inner guide vane carrier and the guide vane structure 503 .
  • the turbine blade structure 504 is shown in FIG. 5 .
  • the guide vane 503 comprises a radially inner platform and a radially outer platform which partly define the working gas flow passage.
  • Each of the platforms has a trailing or downstream edge region between a trailing edge of an aerofoil of the guide vane to the downstream edge of the platform.
  • the present impingement ring arrangement ( 110 , 120 ), is located radially inwardly of the radially inner platform and in addition ensures a controlled leakage and supply of cooling air to the platform and particularly each platform of the annular array of guide vanes.
  • each of the platforms is supplied with equal amounts of cooling air to ensure the platforms are similarly cooled throughout the turbine's operating envelope.
US14/781,819 2013-04-09 2014-03-06 Impingement ring element attachment and sealing Abandoned US20160040553A1 (en)

Applications Claiming Priority (3)

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EP13162976.8 2013-04-09
EP13162976.8A EP2789803A1 (en) 2013-04-09 2013-04-09 Impingement ring element attachment and sealing
PCT/EP2014/054304 WO2014166676A1 (en) 2013-04-09 2014-03-06 Impingement ring element attachment and sealing

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US20160040553A1 true US20160040553A1 (en) 2016-02-11

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US14/781,819 Abandoned US20160040553A1 (en) 2013-04-09 2014-03-06 Impingement ring element attachment and sealing

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US (1) US20160040553A1 (ru)
EP (2) EP2789803A1 (ru)
CN (1) CN105102765B (ru)
RU (1) RU2633319C2 (ru)
WO (1) WO2014166676A1 (ru)

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US20160017750A1 (en) * 2014-07-18 2016-01-21 Pratt & Whitney Canada Corp. Annular ring assembly for shroud cooling
US20170292407A1 (en) * 2016-04-11 2017-10-12 Rolls-Royce Corporation Impingement plate with stress relief feature
US10677084B2 (en) 2017-06-16 2020-06-09 Honeywell International Inc. Turbine tip shroud assembly with plural shroud segments having inter-segment seal arrangement
US10900378B2 (en) 2017-06-16 2021-01-26 Honeywell International Inc. Turbine tip shroud assembly with plural shroud segments having internal cooling passages
US11365635B2 (en) * 2019-05-17 2022-06-21 Raytheon Technologies Corporation CMC component with integral cooling channels and method of manufacture
US11846193B2 (en) * 2019-09-17 2023-12-19 General Electric Company Polska Sp. Z O.O. Turbine engine assembly

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US10260356B2 (en) * 2016-06-02 2019-04-16 General Electric Company Nozzle cooling system for a gas turbine engine

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US10746048B2 (en) 2014-07-18 2020-08-18 Pratt & Whitney Canada Corp. Annular ring assembly for shroud cooling
US20170292407A1 (en) * 2016-04-11 2017-10-12 Rolls-Royce Corporation Impingement plate with stress relief feature
US10677084B2 (en) 2017-06-16 2020-06-09 Honeywell International Inc. Turbine tip shroud assembly with plural shroud segments having inter-segment seal arrangement
US10900378B2 (en) 2017-06-16 2021-01-26 Honeywell International Inc. Turbine tip shroud assembly with plural shroud segments having internal cooling passages
US11181006B2 (en) 2017-06-16 2021-11-23 Honeywell International Inc. Turbine tip shroud assembly with plural shroud segments having inter-segment seal arrangement
US11365635B2 (en) * 2019-05-17 2022-06-21 Raytheon Technologies Corporation CMC component with integral cooling channels and method of manufacture
US11846193B2 (en) * 2019-09-17 2023-12-19 General Electric Company Polska Sp. Z O.O. Turbine engine assembly

Also Published As

Publication number Publication date
CN105102765A (zh) 2015-11-25
EP2984293B1 (en) 2017-08-30
EP2789803A1 (en) 2014-10-15
RU2015142995A (ru) 2017-05-11
WO2014166676A1 (en) 2014-10-16
RU2633319C2 (ru) 2017-10-11
CN105102765B (zh) 2017-08-18
EP2984293A1 (en) 2016-02-17

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